Abrégé

A method of fabricating a composite material part, the method including making a consolidated fiber preform, the fibers of the preform being carbon or ceramic fibers and being coated with an interphase; obtaining a consolidated and partially densified fiber preform, the partial densification comprising using chemical vapor infiltration to form a first matrix phase on the interphase; and continuing densification of the fiber preform by infiltrating an infiltration composition containing at least silicon and at least one other element suitable for lowering the melting temperature of the infiltration composition to a temperature less than or equal to 1150° C.

Classes IPC  ?

• C23C 16/00 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD]
• C23C 16/22 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le dépôt de matériaux inorganiques, autres que des matériaux métalliques
• C04B 35/628 - Revêtement des poudres
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 35/83 - Fibres de carbone dans une matrice carbonée

Abrégé

The present invention relates to a device (1) for dispensing a material, said device (1) comprising a body (2) that defines a storage chamber (4) in which the material to be dispensed is present, and a pressurizing chamber (5) comprising a gas generator (20), the pressurizing chamber (5) being separated from the storage chamber (4) by a movable wall (7) that has at least one fragile portion (7a), the storage chamber (4) being delimited by an end wall (2b) of the body that has at least one outlet opening (10) and at least one relief (12), the gas generator (20) being configured to trigger the dispensing of the material out of the body (2) through the outlet orifice (10) by causing the device (1) to pass from a first configuration for storing the material to a second configuration for the end of dispensing of the material, the movable wall (7) being set in movement towards the end wall (2b) in order to break the fragile portion (7a) by impact with the relief during the passage from the first configuration to the second configuration.

Classes IPC  ?

• A62C 13/22 - Extincteurs portatifs sous pression permanente ou mis sous pression immédiatement avant l'emploi où la pression de gaz est produite par réaction chimique avec des substances incendiaires pour produire une pression de gaz
• A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice
• B65D 83/34 - Nettoyage ou prévention de l'obstruction de l'orifice de sortie
• A62C 13/02 - Extincteurs portatifs sous pression permanente ou mis sous pression immédiatement avant l'emploi où la pression de gaz est produite par réaction chimique
• B05B 9/08 - Appareillages pouvant être portés par une personne, p. ex. du type dorsal
• B05B 15/02 - Systèmes ou dispositifs pour nettoyer des orifices d'évacuation
• B65D 83/64 - Récipients pour distribuer des contenus liquides ou semi-liquides par pression interne de gaz, c.-à-d. réceptacles aérosols contenant un propulseur avec un contenu et un propulseur séparés par des pistons
• A62C 3/07 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers

Abrégé

A thermochemical treatment installation includes a reaction chamber, at least one gas inlet, and a gas preheater chamber situated between the gas inlet and the reaction chamber. The preheater chamber has a plurality of perforated distribution trays held spaced apart one above another. The preheater chamber also includes, between at least the facing distribution trays, a plurality of walls defining flow paths for a gas stream between said trays.

Classes IPC  ?

• C23C 16/46 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour le chauffage du substrat
• C23C 16/458 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour supporter les substrats dans la chambre de réaction
• C23C 16/455 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour introduire des gaz dans la chambre de réaction ou pour modifier les écoulements de gaz dans la chambre de réaction
• F28C 3/00 - Autres appareils échangeurs de chaleur à contact direct
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• B01J 6/00 - CalcinationCuisson
• B01J 8/02 - Procédés chimiques ou physiques en général, conduits en présence de fluides et de particules solidesAppareillage pour de tels procédés avec des particules immobiles, p. ex. dans des lits fixes
• F28F 13/06 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique
• C23C 16/452 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour produire des courants de gaz réactifs, p. ex. par évaporation ou par sublimation de matériaux précurseurs par activation de courants de gaz réactifs avant l'introduction dans la chambre de réaction, p. ex. par ionisation ou par addition d'espèces réactives
• F27B 5/16 - Aménagement des dispositifs d'alimentation en air ou gaz
• F27D 7/06 - Production ou maintien d'une atmosphère particulière ou du vide dans les chambres de chauffage
• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
• F27D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
• F28F 3/08 - Éléments construits pour être empilés, p. ex. pouvant être séparés pour leur nettoyage
• F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes

Abrégé

The present invention relates to a continuous method for treating gases containing metal chlorides resulting from a ceramic process. The invention is characterized in that it includes the following successive steps: a) hydrolysis of the gas containing metal chlorides resulting from a ceramic process by placing said gas in contact with softened water having a pH ≥ 7, more particularly between 7 and 11, such that a hydrochloric acid solution is produced; b) treatment of the hydrochloric acid solution obtained in step a) by passing same over a weak anion-exchange resin such that the Cl- ions are exchanged for OH- ions and such that an aqueous solution having a pH > 7, more particularly between 7 and 11, is obtained; c) use of the treated solution obtained at step b) in step a).

Classes IPC  ?

• B01D 53/68 - Halogènes ou composés halogénés
• B01D 53/73 - Post-traitement des composants éliminés
• B01J 41/00 - Échange d'anionsUtilisation d'une substance comme échangeur d'anionsTraitement d'une substance en vue d'améliorer ses propriétés d'échange d'anions

Abrégé

A thermostructural composite material part including carbon or ceramic fiber reinforcement densified by a matrix having at least one thin portion in which: the thickness of the part is less than 2 mm, or indeed less than 1 mm; the fiber reinforcement is made as a single thickness of multilayer fabric made of spread yarns having a weight of not less than 200 tex; the fiber volume ratio lies in the range 25% to 45%; and the ratio between the number of layers of the multilayer fabric and the thickness in millimeters of the part is not less than four.

Classes IPC  ?

• F02K 9/97 - Tuyères de fusée
• C04B 35/52 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbone, p. ex. graphite
• C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
• C04B 35/628 - Revêtement des poudres
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• D06C 29/00 - Finissage ou apprêtage de tissus textiles non prévus dans les autres groupes de la présente sous-classe
• F02K 1/82 - Parois des tubulures de jet, p. ex. chemises

Abrégé

The present invention relates mainly to substantially cylindrical gas-generating pyrotechnical monolithic blocks, characterised by having: a thickness no lower than 10 mm, an equivalent diameter no lower than 10 mm, and a porosity lower than 5%; and a composition, given as weight percentages, which contains, for at least 94% of the weight thereof: + 77.5% to 92.5% of guanidine nitrate, + 5% to 10% of basic copper nitrate, and + 2.5% to 12.5% of at least one inorganic titanate with a melting temperature higher than 2100 K. Said blocks are particularly efficient, in particular as regards their combustion temperature and speed (low), the ease with which they can be obtained, and their gas yield.

Classes IPC  ?

• C06B 23/00 - Compositions caractérisées par des constituants non explosifs ou non thermiques
• C06B 45/00 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit
• C06D 5/06 - Production de gaz sous pression, p. ex. pour cartouches de mine, cartouches de mise à feu, fusées par réaction de plusieurs solides

Abrégé

A process for manufacturing a multiperforated composite part comprises the following steps: - positioning a sandblasting mask (250) on a preform (110) comprising a fibrous texture impregnated with a polymerized ceramic precursor resin, said mask comprising a plurality of openings (251) corresponding to the perforations to be made in the preform (110), - spraying abrasive particles at high speed onto the surface of the mask (250) so as to perforate the preform (110) exposed in the openings of said mask, - pyrolysis of the multiperforated perform so as to form a ceramic matrix in the multiperforated fibrous texture.

Classes IPC  ?

• B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
• C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
• C04B 35/628 - Revêtement des poudres
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 38/00 - Mortiers, béton, pierre artificielle ou articles de céramiques poreuxLeur préparation

Abrégé

A combined steering and drag reduction device for a missile is disclosed. The device includes a base and an upper part which are arranged in succession along a main axis of navigation of the missile. Advantageously, the device also includes a pressurized-gas generator and at least one lateral thruster having at least one nozzle configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis. The at least one lateral thruster also has at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis.

Classes IPC  ?

• F42B 10/66 - Pilotage par variation de l'intensité ou de la direction de la poussée
• F42B 15/01 - Dispositions pour le guidage ou le pilotage sur les projectiles autopropulsés ou les missiles
• F42B 10/40 - Dispositions pour augmenter la portée par la combustion d'une charge à vitesse de combustion lente, p. ex. projectiles du type à écoulement par le culot
• F42B 10/00 - Moyens pour influencer, p. ex. pour améliorer, les propriétés aérodynamiques de projectilesDispositions sur les projectiles pour la stabilisation, le pilotage, le freinage de la chute, la réduction ou l'augmentation de la portée
• F42B 15/00 - Projectiles autopropulsés, p. ex. roquettesMissiles

Abrégé

The invention relates to thermochemical treatment equipment (100) which includes: a reaction chamber (140); at least one gas inlet (104); and a gas preheating chamber (110) located between the gas inlet (104) and the reaction chamber (140). The preheating chamber (110) includes a plurality of perforated distribution plates (111-114) that are kept spaced apart, above one another. The preheating chamber (110) also includes, between at least the distribution plates facing one another, a plurality of walls (1110, 1120, 1130) defining gas flow paths between said plates (111-114).

Classes IPC  ?

• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
• C23C 16/455 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour introduire des gaz dans la chambre de réaction ou pour modifier les écoulements de gaz dans la chambre de réaction
• C04B 35/00 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques
• C04B 35/83 - Fibres de carbone dans une matrice carbonée
• C23C 16/452 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour produire des courants de gaz réactifs, p. ex. par évaporation ou par sublimation de matériaux précurseurs par activation de courants de gaz réactifs avant l'introduction dans la chambre de réaction, p. ex. par ionisation ou par addition d'espèces réactives
• F27B 5/16 - Aménagement des dispositifs d'alimentation en air ou gaz
• F27D 7/06 - Production ou maintien d'une atmosphère particulière ou du vide dans les chambres de chauffage
• F27D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
• F28F 3/08 - Éléments construits pour être empilés, p. ex. pouvant être séparés pour leur nettoyage
• F28F 13/06 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique
• F28F 9/02 - Boîtes de distributionPlaques d'extrémité
• F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation

Abrégé

A section (100) of a turbine stator comprising a plurality of blades (110) made from a composite material and each comprising a blade body (111) extending between first and second ends (112, 113). The section further comprises first and second platforms (120, 130) made from composite material, the first platform (120) comprising openings (121) in which the first ends (112) of the blades (110) are engaged and the second platform (130) comprising openings (131) in which the second ends (113) of the blades (110) are engaged. The openings (121) of the first platform (120) have dimensions larger than the dimensions of the first ends (112) of the blades (110) engaged in said openings (121), in such a way as to provide clearance (J) between the first end (112) of each blade (110) and the opening (121). Each first blade end (112) engaged in the opening (121) has dimensions smaller than the dimensions of the blade body (111) in such a way as to define a shoulder (1121) extending around said first end (112). The shoulder has dimensions larger than the dimensions of the openings (121) of the first platform (120).

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

The present invention relates to a method for treating waste gas containing polycyclic aromatic hydrocarbons, comprising a stage of washing by spraying mineral oil in order to trap said hydrocarbons, characterized in that the mineral oil comprises a mixture of aromatic mineral oil and naphthenic mineral oil. The method further comprises the use of a naphthenic mineral oil to reduce the viscosity of an aromatic mineral oil loaded with polycyclic aromatic hydrocarbons, advantageously with an aromatic mineral oil containing at most 30% by volume polycyclic aromatic hydrocarbons.

Classes IPC  ?

• B01D 53/14 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par absorption
• C23C 16/44 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement

Abrégé

The invention relates to : • a sized yarn (1) intended to undergo a textile operation comprising: • - a plurality of ceramic and/or carbon fibres (2), • - an interphase coating (3, 3') that covers the fibres, and • - a film (4) that covers the interphase coating comprising a linear-chain polysiloxane.

Classes IPC  ?

• D02G 3/16 - Filés ou fils faits de substances minérales

Abrégé

A part (300) made from an oxide/oxide composite material comprising a fibrous reinforcement (310) consisting of a plurality of layers of warp threads (312) and of weft threads (311) linked together by three-dimensional weaving, the spaces between the reinforcing threads being filled by a matrix of refractory oxide (320). The part is characterized in that the fibrous reinforcement has a fabric weave selected from one of the following weaves: interlock, multi-layer, multi-satin and multi-twill, and a thread count in the warp and weft of between 4 and 20 threads/cm. The fibrous reinforcement further has a volume density of fibres of between 40% and 51%.

Classes IPC  ?

• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• D03D 11/00 - Tissus doubles ou à couches multiples non prévus ailleurs

Abrégé

A method of fabricating a composite material casing for a gas turbine engine, the method including making an outer shroud including a platform and a flange, making an inner shroud of smaller diameter than the outer shroud and including a platform and a flange, making a plurality of casing arms, each including a blade that is terminated at each radial end by a respective platform, arranging a plurality of openings in the respective platforms of the shrouds, each opening serving to receive a platform of a casing arm, and assembling the casing arms with the outer shroud and with the inner shroud by inserting the platforms of the casing arms in the openings of the shrouds. A composite material casing is obtained by such a method.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

The invention relates to a composite composition for solid propellant comprising a) an energy charge, b) a possible reducing charge, c) an energetic binder comprising an energetic plasticiser based on nitric esters and a stabiliser of the nitric esters, and d) a cross-linking system, characterised in that the stabiliser of the nitric esters is selected from the epoxidised fatty acid esters.

Classes IPC  ?

• C06B 23/00 - Compositions caractérisées par des constituants non explosifs ou non thermiques
• C06B 45/10 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit comportant des particules solides dispersées dans une solution solide ou une matrice le composé étant une solution solide ou matrice contenant un composant organique le composant organique contenant une résine

Abrégé

The present invention relates to composite pyrotechnical products, in particular to propellant powders for barrelled weapons, in which the composition, expressed in weight percentages, includes: 78 % to 90 %, advantageously 80 % to 86 %, of organic energy loads; and 10 % to 22 % of a polymer gum, selected among the polyurethane-polyester gums, the polyurethane-polyether gums and the mixtures thereof, in which the average molecular weight by number is higher than 20,000 g/mol and in which the Mooney viscosity is from 20 to 70 ML (5 + 4) at 100 °C. The invention also relates to the method for obtaining said products. Said products are particularly useful given the properties thereof and how easily they can be obtained.

Classes IPC  ?

• C06B 45/10 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit comportant des particules solides dispersées dans une solution solide ou une matrice le composé étant une solution solide ou matrice contenant un composant organique le composant organique contenant une résine
• C06B 21/00 - Appareils ou méthodes pour la mise en œuvre des explosifs, p. ex. mise en forme, coupage, séchage

Abrégé

The present invention relates to a composite pyrotechnical product, in particular a propellant powder for barrelled weapons, containing organic energy loads in a crosslinked binder. The composition of said product, expressed in weight percentages, typically includes: 78 % to 90 %, advantageously 80 % to 86 %, of organic energy loads; and 10 % to 22 % of an energetic crosslinked binder obtained by crosslinking, via only 8 % to 12 % of the azide functions thereof, a glycidyl polyazide having an average molecular weight of 700 to 3,000 g/mol, with at least one crosslinking agent containing at least two propargyl functions in the chemical formula thereof, in the presence of a polymer gum, selected among the polyurethane-polyester gums, the polyurethane-polyether gums and the mixtures thereof, in which the average molecular weight by number is higher than 20,000 g/mol and in which the Mooney viscosity is from 20 to 70 ML (5 + 4) at 100 °C; said at least one polymer gum making up 1 wt % to 5 wt % of the composition of said pyrotechnical product. The invention also relates to the method for obtaining said products. Said products are particularly useful given the properties thereof and how easily they can be obtained.

Classes IPC  ?

• C06B 21/00 - Appareils ou méthodes pour la mise en œuvre des explosifs, p. ex. mise en forme, coupage, séchage
• C06B 45/10 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit comportant des particules solides dispersées dans une solution solide ou une matrice le composé étant une solution solide ou matrice contenant un composant organique le composant organique contenant une résine

Abrégé

The subject matter of the present invention is: polymers with azide end functions of formula (V): - the production of such polymers + from a hydroxytelechelic polymer of formula (I): OH-P-OH, + from an azido alcohol of formula (II): HO-R1N3, and + from a diisocyanate of formula (III): O=C=N-R2-N=C=O; - the solid propellants which can be obtained from said polymers. Said propellants are capable of containing energetic fillers of any type, in particular energetic fillers with intrinsic acidity.

Classes IPC  ?

• C08F 136/14 - Homopolymères de composés possédant un ou plusieurs radicaux aliphatiques non saturés, l'un au moins contenant plusieurs liaisons doubles carbone-carbone le radical ne contenant que deux doubles liaisons carbone-carbone conjuguées contenant des éléments autres que le carbone ou l'hydrogène
• C08F 8/30 - Introduction d'atomes d'azote ou de groupes contenant de l'azote
• C08G 65/333 - Polymères modifiés par post-traitement chimique avec des composés organiques contenant de l'azote
• C08G 63/685 - Polyesters contenant des atomes autres que le carbone, l'hydrogène et l'oxygène contenant de l'azote
• C08G 63/91 - Polymères modifiés par post-traitement chimique
• C08J 3/24 - Réticulation, p. ex. vulcanisation, de macromolécules
• C06B 23/00 - Compositions caractérisées par des constituants non explosifs ou non thermiques

Abrégé

The present invention relates to a method for inerting a tank (S) of fuel (6) of a moving aircraft and to a related device (1a, 1b, 1c). Said method includes dispensing an inerting gas into said tank (5) while the volume (V) of fuel (6) in said tank (5) decreases as a result of the engine(s) of said aircraft consuming the fuel. Said method characteristically includes: keeping at least one tank (2) pressurized using an inerting gas consisting of at least 90% nitrogen in volume, generated by combusting and/or decomposing separate solid loads (8), at least some of said loads (8) being, for the purpose of keeping said tank under pressure, ignited differently and independently from one another in the patent application; and continuously supplying pressurized inerting gas from said at least one tank (2) into the free space (v) of said tank (5) of fuel (6) in expansion, such as to inert said free space (v). The pressure inside said tank (2) is monitored while said supplying of inerting gas is carried out.

Classes IPC  ?

• B64D 37/32 - Mesures de sécurité non prévues ailleurs, p. ex. contre les explosions
• A62D 1/06 - Compositions pour éteindre les incendiesEmploi de produits chimiques pour éteindre les incendies contenant des composants produisant du gaz par réaction chimique
• B01J 7/00 - Appareillage pour la production de gaz
• B01J 19/14 - Production de mélanges de gaz inertesUtilisation des gaz inertes en général
• B65D 90/44 - Moyens pour diminuer le volume disponible pour les vapeurs ou pour réduire la formation de vapeurs à l'intérieur des réceptacles en employant un gaz inerte pour remplir le volume libre au-dessus du liquide ou entre les éléments de la charge
• C06D 5/06 - Production de gaz sous pression, p. ex. pour cartouches de mine, cartouches de mise à feu, fusées par réaction de plusieurs solides

Abrégé

The invention relates to a method for connecting the end portion of a prefabricated skirt (22) to an engine body casing (10) near a base thereof, wherein said method includes: moving the end portion (22b) of the skirt (22) into a position with circumferential clearance around the engine body casing (10) near the base (14); keeping the skirt in position relative to the engine body casing; closing both ends of an annular space (46) between the end portion (22b) of the skirt (22) and the engine body casing (10); injecting an elastomer into said annular space (46); and cross-linking the elastomer.

Classes IPC  ?

• B29C 65/54 - Application d'un adhésif entre des éléments pré-assemblés
• F02K 9/36 - Supports des charges de propergols
• B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie

Abrégé

An industrial facility (500) for chemical vapour infiltration of porous substrates comprising a sealed reaction chamber (110), a supply circuit (400), a discharge circuit (200) connected to the reaction chamber (110) and a heat exchanger (210). The facility further comprises: - an accelerated cooling circuit (300) comprising at least one inlet (301a) in selective communication with the outlet of the heat exchanger (210), and an outlet (301b) in selective communication with the supply circuit (400), - first connection means (2110; 2030) for connecting the discharge circuit (200) to the inlet of the heat exchanger (210), - second connection means (3010) for directly or indirectly connecting the inlet (301a) of the accelerated cooling circuit (300) to the outlet of the heat exchanger (210) when the reaction chamber (110) is supplied with said at least one cooling gas.

Classes IPC  ?

• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
• C23C 16/44 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement
• C23C 16/455 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour introduire des gaz dans la chambre de réaction ou pour modifier les écoulements de gaz dans la chambre de réaction
• C23C 16/46 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour le chauffage du substrat

Abrégé

A method of fabricating a composite material part comprises fiber reinforcement densified by a matrix. The method comprises the following steps: making a fiber fabric by weaving yarns having an initial mean fiber percentage; and densifying the fiber fabric with a matrix. The fiber fabric is subjected, prior to densification, to one or more jets of water under pressure so as to reduce the mean fiber percentage in the fabric to a value lying in the range 20% to 45%.

Classes IPC  ?

• C23C 16/02 - Pré-traitement du matériau à revêtir
• D06C 21/00 - Retrait compressif des tissus
• C04B 35/628 - Revêtement des poudres
• D06C 29/00 - Finissage ou apprêtage de tissus textiles non prévus dans les autres groupes de la présente sous-classe
• C04B 35/571 - Céramiques fines obtenues à partir de précurseurs polymères
• B32B 18/00 - Produits stratifiés composés essentiellement de céramiques, p. ex. de produits réfractaires
• D03D 25/00 - Tissus non prévus ailleurs

Abrégé

System (20) for the emergency starting of aircraft turbomachines, comprising at least one solid-fuel gas generator (22), an electrically operated ignition device (24), a computer (28) connected to the ignition device, and at least two independent starters (18) each one intended to start a turbomachine, each starter comprising a turbine (38) for driving a shaft (34) intended to be coupled to a shaft (54) of the corresponding turbomachine, the gas outlet of the generator being connected to the inlet (44) of the turbine of each starter by one and the same distribution valve (26) connected to the computer (28).

Classes IPC  ?

• F01D 19/00 - Démarrage des "machines" ou machines motricesDispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
• F02C 7/272 - Entraînement du rotor pour le démarrage par fluide produit par des cartouches
• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine

Abrégé

The invention relates to a process for fabricating a composite part, comprising the steps of: - producing a consolidated fibrous preform, the fibres of the preform being carbon fibres or ceramic fibres and being coated with an interphase, - obtaining a consolidated and partially densified fibrous preform, the partial densification comprising the formation, on the interphase, on a first matrix phase obtained by chemical vapour infiltration, and - continuation of the densification by infiltration of the fibrous preform with an infiltration composition containing at least silicon and at least one other element capable of lowering the melting point of the infiltration composition to a temperature less than or equal to 1150°C.

Classes IPC  ?

• C04B 35/573 - Céramiques fines obtenues par frittage par réaction
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 41/45 - Revêtement ou imprégnation
• C04B 41/50 - Revêtement ou imprégnation avec des substances inorganiques
• C04B 41/51 - Métallisation
• C04B 35/628 - Revêtement des poudres
• C22C 29/00 - Alliages à base de carbures, oxydes, borures, nitrures ou siliciures, p. ex. cermets, ou d'autres composés métalliques, p. ex. oxynitrures, sulfures

Abrégé

A space vehicle (1), in particular a satellite or a probe, capable of executing high-thrust maneuvers or high specific impulse maneuvers. According to the invention, the space vehicle (1) includes at least one solid-propellant chemical thruster (10-14) and at least one electric thruster (20-24).

Classes IPC  ?

• B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
• B64G 1/42 - Aménagements ou adaptations des systèmes fournissant l'énergie
• F02K 9/22 - Forme ou structure des charges de propergols solides du type à combustion sur leur surface frontale
• B64G 1/10 - Satellites artificielsSystèmes de tels satellitesVéhicules interplanétaires
• B64G 1/24 - Appareils de guidage ou de commande, p. ex. de commande d'assiette
• F03H 1/00 - Utilisation du plasma pour produire une poussée propulsive par réaction

Abrégé

The present invention concerns a composite solid propellant of which the composition contains an oxidising charge and a reducing charge in a binder. The reducing charge characteristically consists of particles of at least one aluminium/magnesium alloy or consists of a mixture of particles of at least one aluminium/magnesium alloy and aluminium particles; said reducing charge containing a total quantity of magnesium that represents less than 3 %, and advantageously less than 1 %, of the mass of same. The presence of such a low level of magnesium helps reduce the thrust instabilities of a rocket engine operating with said propellant and helps increase the propulsive performances of said rocket engine.

Classes IPC  ?

• C06B 33/06 - Compositions contenant des particules de métal, alliage, bore, silicium, sélénium ou tellure avec au moins un matériau fournissant de l'oxygène, qui est soit un oxyde métallique, soit un sel, organique ou inorganique, susceptible de donner un oxyde métallique le matériau étant un sel inorganique d'un composé d'halogène et d'oxygène
• C06B 45/10 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit comportant des particules solides dispersées dans une solution solide ou une matrice le composé étant une solution solide ou matrice contenant un composant organique le composant organique contenant une résine

Abrégé

The present invention mainly concerns a method for delivering a liquid (L) contained in a tank (1), said tank (1) having at least one port (2) for delivering said liquid (L) sealed by a seal (3) that can be retracted when a threshold pressure is applied to said liquid (L), comprising: the combustion of at least one pyrotechnic charge (7) in order to generate combustion gases, the pressurisation of said liquid (L) under the action of said combustion gases, and the retraction of said retractable seal (3) from said at least one delivery port (2) and the delivery of said pressurised liquid (L), characterised in that the flow of generated combustion gases during the delivery of said liquid (L) provides almost constant pressurisation of said liquid (L) and therefore the delivery of said liquid (L) at an almost constant flow rate; the pressure of said liquid (L) during the delivery of said liquid varying by a maximum of only +/- 30 %, advantageously by a maximum of only +/- 20 %, and very advantageously by a maximum of only +/- 10 %, relative to the initial of same at the time when said seal or seals (3) is/are retracted; and in that it is implemented in a device (100; 101; 102) comprising said tank (1) and at least one pyrotechnic gas generator (15; 16; 17) containing said at least one pyrotechnic charge (7; 7'; 70; 700; 700'); said at least one pyrotechnic gas generator (15; 16; 17) being connected to said tank (1) and a movable member (4) for separating the generated combustion gases and said liquid (L) being provided inside said device (100; 101; 102).

Classes IPC  ?

• A62C 13/22 - Extincteurs portatifs sous pression permanente ou mis sous pression immédiatement avant l'emploi où la pression de gaz est produite par réaction chimique avec des substances incendiaires pour produire une pression de gaz
• A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice
• A62C 35/08 - Réservoirs se brisant ou s'ouvrant sous l'action d'une charge explosive

Abrégé

The invention relates to an assembly (100) comprising a first part (10) and a second part (20) made of composite material that are held against one another by at least one fastening system (50) comprising a rivet (30) that has a countersunk head (31) from which there extends a shank (32) that has a widened end (320) and a washer (40) that engages with the widened end (320) of the shank (32) of the rivet (30). The head (31) of the rivet (30) bears against a countersunk hole (12) made in the first part (10), the washer (40) bearing against the second part (20). The washer (40) has, on its face (43) opposite the one (42) bearing against the second part (20), a portion (430) with a conical shape. The washer (40) also has a central countersunk hole (410) on the surface of which the widened end (320) of the shank (32) of the rivet (30) rests.

Classes IPC  ?

• F16B 19/05 - Chevilles fixées par collerettes embouties
• F16B 19/10 - Rivets creuxRivets en plusieurs morceaux fixés par action mécanique

Abrégé

A part comprising a substrate (10), at least one portion of which adjacent to a surface of the substrate is made of a refractory material containing silicon, is protected by an environmental barrier (20) formed on the surface of the substrate and having at least one self-healing layer (22) containing a rare-earth silicate. At least 90 mol% of the self-healing layer (22) is formed from a system consisting of 30 mol% to at most 80 mol% of at least one rare-earth silicate RE2Si2O7, RE being a rare earth, and at least 20 mol% to 70 mol% of manganese oxide MnO; and at most 10 mol% of the self-healing layer (22) is formed from one or more oxides, except MnO, having a eutectic point with SiO2 lower than or equal to 1595°C, the self-healing layer (22) exhibiting a liquid phase having a self-healing function in at least the entire temperature range extending from 1200°C to 1400°C while preserving a predominantly solid phase.

Classes IPC  ?

• C04B 41/85 - Revêtement ou imprégnation avec des substances inorganiques
• C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

A pyrotechnic charge (1) for a pyrotechnic gas generator comprises a plurality of blocks (12) of pyrotechnic material stacked in layers (10), each block (12) being delimited by two main faces substantially orthogonal to the direction (A) of the stack. In this pyrotechnic charge (1), each layer (10) of the stack comprises at least two distinct blocks (12) of pyrotechnic material each one forming an angular sector of an annulus or of a disc, said blocks being assembled to form an annulus (14) and/or a disc.

Classes IPC  ?

• F42B 3/04 - Cartouches de sautage, c.-à-d. enveloppes avec explosif pour la production de gaz sous pression
• F02K 9/18 - Forme ou structure des charges de propergols solides du type à combustion sur leur surface interne comportant une cavité interne en forme d'étoile ou en forme analogue
• F42B 5/16 - Cartouches, c.-à-d. projectile et douille avec charge propulsive formant un tout caractérisées par la composition ou les dimensions géométriques ou la forme de la charge propulsive ou de la poudre
• F42B 30/12 - Obus de mortiers avec la possibilité d'ajouter des charges propulsivesObus de mortiers avec la possibilité de faire varier la longueur

Abrégé

An assembly (100) comprising a first part (10) and a second part (20) made from a composite material held together by at least one fixing system (50) comprising a screw (30) comprising a countersunk head (31) from which a threaded portion (32) extends and a nut (40) comprising a countersunk head (41) from which a barrel (42) extends comprising a tapped hole (43) that engages with the threaded portion (32) of the screw (30). The head (31) of the screw (30) bears against a recess (12) provided in the first part (10). The head of the nut (41) engages in a recess (22) provided in the second part (20). The fixing system (50) is capable of making each head (31, 41) tilt towards the recess (12; 22) in which it is housed when the fixing system (50) expands axially.

Classes IPC  ?

• F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
• F16B 37/14 - Écrous-chapeauxChapeaux d'écrous ou de boulons

Abrégé

A rotor disc blade (10) for a turbomachine made from composite material comprising a fibrous reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade (10) comprises a portion that forms the airfoil (12) and the blade root (14) forming a single part, the blade root (14) having two substantially planar opposing side flanks (22, 24) that are formed in the respective extensions of the pressure (12a) and suction (12b) surfaces of the airfoil (10). The blade root (14) is gripped between two metal plates (26, 28) fixed against the side flanks (22, 24) of the blade root by a screw (30) and a nut (40) passing through the plates (26, 28) and the blade root (14). The screw (30) comprises a head (31) bearing on one (26) of the two plates. The nut (40) comprises a head (41) bearing on the other plate (28). The screw and the nut (30, 40) apply, to the metal plates (26, 28), a minimum clamping force capable of taking up, by friction between the metal plates (26, 28) and the side flanks (22, 24) of the blade root (14), a predefined centrifugal force applied to the blade (10).

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

The invention concerns: a method of obtaining a solid form containing heat-stable borazane, said solid form being capable of generating hydrogen by thermal decomposition or by a self-sustained combustion reaction, the solid form containing heat-stable borazane; and a hydrogen-generating method comprising the thermal decomposition or self-sustained combustion of the solid form containing heat-stable borazane. According to the invention, within said borazane-containing solid form, the borazane is stabilized thermally as a result of an oxidized layer being formed on the surface thereof.

Classes IPC  ?

• C01B 3/04 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par décomposition de composés inorganiques, p. ex. de l'ammoniac
• C06D 5/06 - Production de gaz sous pression, p. ex. pour cartouches de mine, cartouches de mise à feu, fusées par réaction de plusieurs solides
• C06B 45/30 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit comportant un composant revêtu le composant de base contenant un composant inorganique explosif ou thermique
• C06D 5/04 - Production de gaz sous pression, p. ex. pour cartouches de mine, cartouches de mise à feu, fusées par auto-décomposition de substances sans mélange

Abrégé

The invention relates to a pyrotechnical gas generator (10) for actuating a cylinder (100), including a body defining a combustion chamber (12) which contains a main pyrotechnical load (14), and an igniter (16, 18) for initiating the combustion of said main pyrotechnical load (14). The pyrotechnical gas generator (10) includes at least one retarding chamber (22) suitable for communicating with the combustion chamber (12) via at least one inlet (62), and the retarding chamber (22) is provided with at least one outlet (63) for the passage of the gases outside the gas generator, wherein said outlet is provided with a seal (73) suitable for moving from a closed state to an open state when the pressure inside the retarding chamber reaches a maximum breaking pressure (P1).

Classes IPC  ?

• F42B 3/00 - Cartouches de sautage, c.-à-d. enveloppes avec explosif
• F15B 15/19 - Vérins pyrotechniques
• F42B 3/04 - Cartouches de sautage, c.-à-d. enveloppes avec explosif pour la production de gaz sous pression

Abrégé

A holding tool (100) for holding a porous rotating preform comprises a lower ring (110) and an upper ring (120) held coaxially above the lower ring by at least one spacer member (130). Each ring (110; 120) comprises, on the outer surface of same, a bearing (111; 121) intended to be in contact with a part of a porous preform (10). At least one (110) of the two rings (110, 120) comprises a cylindrical bearing, the outer surface of each ring (110; 120) being further coated with a compressible material (112, 122) capable of creating sliding contact with the part of the porous preform with which it is in contact.

Classes IPC  ?

• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
• C23C 16/458 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour supporter les substrats dans la chambre de réaction

Abrégé

A method for densifying a porous substrate (50) by means of a matrix, said method comprising the steps of: - fractionation of the porosity present in the porous substrate in such a way as to form, in said substrate, a microporosity network, said fractionation being carried out with a filling composition comprising at least one carbon phase or one carbide phase accessible via the microporosity network, - reactive gaseous-phase chemical infiltration of the microporosity network formed by the filling material, said infiltration being carried out with a reactive gaseous composition free of carbon and comprising at least one element capable of reacting with the carbon of the filling composition in order to form a carbide (53).

Classes IPC  ?

• C04B 35/56 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures
• C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
• C04B 35/573 - Céramiques fines obtenues par frittage par réaction
• C04B 35/628 - Revêtement des poudres
• C04B 35/65 - Frittage par réaction de compositions contenant un métal libre ou du silicium libre
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 35/83 - Fibres de carbone dans une matrice carbonée
• C04B 35/563 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de bore

Abrégé

The present invention relates to a method for obtaining solutions that contain 1,2,4-triazole-5-one (3) (OTA) in concentrated sulphuric acid, said method using 3-amino-1,2,4-triazole (1) (ATA) as a precursor of OTA (3); to said solutions and to a method for preparing 3-nitro-1,2,4-triazole-5-one (4) (ONTA) from said solutions.

Classes IPC  ?

• C07D 249/12 - Atomes d'oxygène ou de soufre
• C07D 249/14 - Atomes d'azote

Abrégé

A device for modulating a gas ejection section (100) comprising a partial sealing member (111) for partially sealing a nozzle neck (13), a control guide (112) for controlling the sealing member (111), a main piston (120) and a priming piston (130). The control guide (112) is movable between a retracted position in which the partial sealing member (111) is retracted relative to the nozzle neck (13) and a sealing position in which the partial sealing member (111) is in contact with the nozzle neck (13). The priming piston (130) is movable between an idle position and a priming position of the main piston (120) when the pressure in the modulation device reaches a first predefined value. The main piston (120) is movable between a first locked position that locks the movement of the control guide (112) in the retracted position of same and a second locked position that locks the control guide (112) when the pressure in the modulation device reaches a second predefined value lower than the first predefined value.

Classes IPC  ?

• F02K 9/86 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères à section réglable

Abrégé

A nozzle having a variable neck section for a spacecraft thruster, comprising a cylindrical housing having a neck (30) of which the opening diameter is smaller than the diameter of the housing, and a needle (24) capable of sliding into the housing between a front position of high-flow operation in which a nose (28) is recessed relative to the neck of the housing and a back position of low-flow operation in which the nose is abutted against the neck, the needle comprising a rod (26) intended to slide into the housing in the nozzle, the rod ending with the nose having a decreasing diameter. The nose of the rod is capable of coming into abutment against the neck of the housing in the nozzle forming a seat, and comprises at least two axial grooves (34) provided on the outer periphery of same to allow gas to flow when the nose axially abuts against the neck of the housing in the nozzle.

Classes IPC  ?

• F02K 9/86 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères à section réglable
• F02K 1/08 - Variation de la section utile de la tubulure de jet ou de la tuyère par déplacement axial ou déformation transversale d'un organe interne, p. ex. du cône d'échappement
• F02K 9/80 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée

Abrégé

The present invention concerns a method (and the associated device) for supplying a fuel cell (3) with a hydrogenated gas (G), consisting essentially of hydrogen, at a pressure lower than or equal to 5.105 Pa and at a temperature lower than 250°C, and generally lower than 200°C. Said method comprises: a) burning at least one hydrogenated-gas generating solid pyrotechnic charge (7) in order to produce a hot, pressurised hydrogenated gas (GO) containing at least 70 mol% hydrogen; b) supplying and operating an open-cycle two-reservoir heat engine (2) with at least one portion of said hot, pressurised hydrogenated gas (GO) containing at least 70 mol% hydrogen, that has been produced; said heat engine (2) then delivering an expanded and cooled hydrogenated gas (Gl) corresponding to said at least one portion of this hydrogenated gas (GO) that has been produced; c) supplying said fuel cell (3) with a hydrogenated gas (G) corresponding to at least one portion of said hydrogenated gas (Gl) delivered by said heat engine (2), expanded to a pressure lower than or equal to 5.105 Pa and cooled to a temperature lower than 250°C, and generally lower than 200°C. Said method has a particularly advantageous energy balance.

Classes IPC  ?

• C06D 5/06 - Production de gaz sous pression, p. ex. pour cartouches de mine, cartouches de mise à feu, fusées par réaction de plusieurs solides
• C01B 3/06 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés inorganiques comportant un hydrogène lié électropositivement, p. ex. de l'eau, des acides, des bases, de l'ammoniac, avec des agents réducteurs inorganiques

Abrégé

A space propulsion module in particular for equipping spacecraft such as satellites, probes, or indeed upper stages of rockets. According to the invention, this space propulsion module comprises a solid-fuel chemical thruster (10), having a main body (11), and at least one electric thruster (30), said at least one electric thruster (30) being mounted on said main body (11) of the solid-fuel chemical thruster (10).

Classes IPC  ?

• B64G 1/00 - Véhicules spatiaux
• B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
• B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
• F02K 9/34 - CartersChambres de combustionLeurs chemises
• F03H 1/00 - Utilisation du plasma pour produire une poussée propulsive par réaction

Abrégé

The invention relates to a nozzle with a movable divergent, comprising a fixed throat (210) forming a spherical joint and a divergent (220) with an upper part that is movably mounted around the throat (210). An annular lubrication chamber (230) is arranged between the throat (210) and the upper part of the divergent (220), the chamber comprising a grease seal (231). The nozzle also comprises: an annular lamination element (310) arranged between the throat (210) and the divergent (220), downstream from the lubrication chamber (230), said lamination element consisting of a refractory material; and an annular thermal protection element (320) arranged between the throat (210) and the divergent (220), upstream from the lamination element (310), said thermal protection element (320) closing the lubrication chamber (230) in the lower part (230b) thereof.

Classes IPC  ?

• F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet
• F02K 9/84 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères mobiles

Abrégé

A turbine nozzle or a compressor diffuser includes sectors made of CMC material, each having an inner platform, an outer platform, and airfoils. An abradable material support ring is made up of sectors, each presenting upstream and downstream attachment tabs. Each inner platform presents on the inside an upstream hook and a downstream hook, and the abradable material support ring is supported by the nozzle or the diffuser by mutually engaging without fastening together firstly the end portions of the upstream attachment tabs and the upstream hooks and secondly the end portions of the downstream attachment tabs and the downstream hooks.

Classes IPC  ?

• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 11/12 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator utilisant un élément de friction allongé, p. ex. un élément d'usure, déformable ou contraint de façon élastique
• F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes

Abrégé

The invention relates to a method for producing a curved honeycomb structure, comprising the following steps: producing a deployable fibrous structure (100) by means of the multi-layer weaving of a plurality of layers of warp yarns and a plurality of layers of weft yarns, said fibrous structure comprising separating zones which extend through the thickness of the fibrous structure and are spaced from one another by linking portions between multiple layers of weft yarns, the linking portions being offset by one or more weft yarns in a direction parallel to that of the layers of weft yarns between each series of weave planes; impregnating the fibrous structure (100) with a precursor resin of a pre-determined material; deploying the fibrous structure (100) on a holding tool (50) such as to form, in the fibrous structure, a cell or honeycomb in each separating zone, said tool also having a curved shape corresponding to the shape of the honeycomb structure to be produced; polymerising the resin of the fibrous structure such as to form a curved honeycomb structure comprising a plurality of cells or honeycombs.

Classes IPC  ?

• B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
• B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
• B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• D03D 25/00 - Tissus non prévus ailleurs

Abrégé

The invention relates to a method for producing a curved sound attenuation panel, comprising the following steps: impregnating a fibrous structure defining a honeycomb structure (150) with a ceramic precursor resin; polymerising the ceramic precursor resin while maintaining the fibrous structure on a tool having a curved shape corresponding to the end shape of the honeycomb structure (150); applying first and second skins to the honeycomb structure (150), each skin being formed by a fibrous structure (200; 300) impregnated with a ceramic precursor resin and each skin being applied to the honeycomb structure before or after polymerisation of the resin of the skins; pyrolysing the assembly formed by the honeycomb structure and the first and second skins; and densifying the assembly by means of gas-phase chemical infiltration.

Classes IPC  ?

• B32B 18/00 - Produits stratifiés composés essentiellement de céramiques, p. ex. de produits réfractaires
• C04B 35/571 - Céramiques fines obtenues à partir de précurseurs polymères
• C04B 35/573 - Céramiques fines obtenues par frittage par réaction
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 37/00 - Liaison des articles céramiques cuits avec d'autres articles céramiques cuits ou d'autres articles, par chauffage
• E04C 2/36 - Éléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux caractérisés par la forme ou la structure composés de plusieurs éléments séparés analogues à des feuilles séparés par des bandes de matériaux disposées transversalement, p. ex. panneaux alvéolaires
• G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
• C04B 35/83 - Fibres de carbone dans une matrice carbonée
• C04B 35/111 - Céramiques fines
• C04B 35/48 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base d'oxydes à base d'oxydes de zirconium ou d'hafnium ou de zirconates ou d'hafnates
• F02K 1/82 - Parois des tubulures de jet, p. ex. chemises

Abrégé

The present invention relates to a method of treating silicon carbide fibres comprising the step of chemically treating the fibres with water under homogeneous subcritical conditions or in the vicinity of the critical point at a pressure between the saturation vapour pressure and 30 MPa and at a temperature less than or equal to 400°C in order to selectively eliminate the silicon present at the surface of the fibres and to form a microporous carbon layer. It also relates to a method of fabricating a fibrous preform comprising the formation of a fibrous structure based on treated silicon carbide fibres and the use of this preform for fabricating a composite material part.

Classes IPC  ?

• C04B 35/626 - Préparation ou traitement des poudres individuellement ou par fournées
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 35/628 - Revêtement des poudres
• C23C 16/02 - Pré-traitement du matériau à revêtir
• C23C 16/26 - Dépôt uniquement de carbone
• C04B 41/52 - Revêtement ou imprégnation multiple

Abrégé

The invention relates to a lightning protection device (200) intended to be fitted to a structure (100) that is to be protected, and comprising: a first coating comprising at least one coat of conducting paint (202), a second coating (204) placed on the surface coating and containing a thermally insulating and electrically conducting material.

Classes IPC  ?

• B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
• F02K 9/97 - Tuyères de fusée
• F02C 7/25 - Prévention ou protection contre l'incendie
• C09D 5/24 - Peintures électriquement conductrices

Abrégé

The invention relates to a cross-linkable elastomer composition comprising a mixture (a) of an elastomer composition based on an ethylene-propylene-diene terpolymer elastomer and (b) between 2 and 14 wt. %, in relation to the total weight of the composition, of an amphiphilic statistical copolymer or a block copolymer of a saturated or unsaturated hydrocarbonated C2-C4 polymer functionalised by a polar functional group comprising a maleic anhydride group. The invention also relates to the cross-linked composition, to the method for the preparation thereof, and to the use of same as thermal protection and/or internal sealing of a composite material and/or for accommodating the mechanical deformations of said composite material. The invention further relates to an assembly comprising (A) a structure consisting of a composite material and (B) a coating layer consisting of a cross-linked elastomer composition according to the present invention, to the production method thereof and to the use of same in the fields of aeronautics or aerospace.

Classes IPC  ?

• C08L 23/16 - Copolymères de l’éthylène et du propylène ou de l’éthylène, du propylène et de diène
• C08L 51/06 - Compositions contenant des polymères greffés dans lesquels le composant greffé est obtenu par des réactions faisant intervenir uniquement des liaisons non saturées carbone-carboneCompositions contenant des dérivés de tels polymères greffés sur des homopolymères ou des copolymères d'hydrocarbures aliphatiques ne contenant qu'une seule liaison double carbone-carbone
• C08L 51/04 - Compositions contenant des polymères greffés dans lesquels le composant greffé est obtenu par des réactions faisant intervenir uniquement des liaisons non saturées carbone-carboneCompositions contenant des dérivés de tels polymères greffés sur des caoutchoucs

Abrégé

The subject matter of the present invention is a pyrotechnic process for providing very highly pure hydrogen (G) and also a device (100) suitable for implementing said process. Said process comprises: the combustion of at least one solid pyrotechnic charge which generates hydrogen-containing gas (4a, 4b, 4c, 4d) for the production of a hot hydrogen-containing gas (G1) under pressure, containing at least 70% by volume of hydrogen; and the purification of at least one part of said hydrogen-containing gas (G1) under pressure, by passage through a metallic membrane for separating the hydrogen (9) maintained at a temperature above 250°C, advantageously between 300 and 600°C, so as to obtain, at the outlet of said membrane (9), a hydrogen-containing gas (G) containing at least 99.99% by volume of hydrogen.

Classes IPC  ?

• C01B 3/06 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés inorganiques comportant un hydrogène lié électropositivement, p. ex. de l'eau, des acides, des bases, de l'ammoniac, avec des agents réducteurs inorganiques
• C06B 47/10 - Compositions dans lesquelles les composants sont conservés séparément jusqu'au moment de l'explosion ou de la combustion, p. ex. explosifs du type "Sprengel"Suspensions d'un composant solide dans une phase liquide normalement non explosive, y compris une phase aqueuse épaissie les composants comportant un propergol binaire un composant contenant du bore libre, un borane organique ou un composé binaire du bore, excepté avec l'oxygène

Abrégé

The subject matter of the present invention is a pyrotechnic process for providing very highly pure hydrogen (G) and also a device (20) suitable for implementing said process. Said process comprises: - the combustion of at least one solid pyrotechnic charge which generates hydrogen-containing gas (2) for the production of a hot hydrogen-containing gas (Gl) under pressure, containing at least 70% by volume of hydrogen; - the cooling of at least one part of said hot hydrogen-containing gas (Gl) under pressure, which is produced, then the expansion of said at least one part of said cooled hydrogen-containing gas (G2); and - the purification of said at least one part of said cooled and expanded hydrogen-containing gas (G3) by passage through a zeolite adsorbent filter (11) so as to obtain, at the outlet of said filter (11), a hydrogen-containing gas (G) containing at least 99.99% by volume of hydrogen.

Classes IPC  ?

• C01B 3/06 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés inorganiques comportant un hydrogène lié électropositivement, p. ex. de l'eau, des acides, des bases, de l'ammoniac, avec des agents réducteurs inorganiques

Abrégé

A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

Device for kneading a paste allowing a paste to be kneaded and extruded reliably and in a stabilized manner notably for the manufacture of explosives, and offering greater ease of maintenance. According to the invention, this paste-kneading device comprises an oblong barrel (10), two shafts (14a, 14b) running parallel to one another within the barrel (10), held and driven at their first ends (15a, 15b) defining the upstream end (AM) by a drive device (12), two screws (20a, 20b) each formed of flights borne by the shafts (14a, 14b), each screw (20a, 20b) comprising at least one transport section (21a‑21d) bearing a main flight (21') for progressing the paste along the two screws (20a, 20b), and an outlet orifice (19) made in the wall of the barrel (10) to discharge the kneaded paste; the kneading device further comprises a retaining device (30) configured to hold each shaft (14a, 14b) at its second end (16a, 16b), defining the downstream end (AV), and allowing it to rotate freely, this retaining device (30) comprising, for each shaft (14a, 14b), a first part (31) secured to said shaft (14a, 14b) and a second part (36) secured to an end cap part (13) of the barrel (10), this end cap part (13) being removable and said first (31) and second (36) parts being configured to engage and disengage freely.

Classes IPC  ?

• B01F 7/08 - Mélangeurs à agitateurs tournant dans des récipients fixes; Pétrins avec agitateurs tournant autour d'un axe horizontal ou incliné à vis sans fin
• B01F 15/00 - Accessoires pour mélangeurs

Abrégé

The present invention relates mainly to a method for synthesising hexanitrohexaazaisowurtzitane. Said method includes the following two steps, carried out in sequence: hexa-N-deallylation of 2,4,6,8,10,12-hexaallyl-2,4,6,8,10,12-hexaazatetracyclo(5.5.0.05'9.03,11)dodecane or hexaallylisowurtzitane (HallylIW), in order to obtain stabilised hexaazaisowurtzitane (HAIW); and nitration of said stabilised hexaazaisowurtzitane (HAIW).

Classes IPC  ?

• C07D 487/22 - Composés hétérocycliques contenant des atomes d'azote comme uniques hétéro-atomes dans le système condensé, non prévus par les groupes dans lesquels le système condensé contient au moins quatre hétérocycles
• C06B 25/34 - Compositions contenant un composé organique nitré le composé étant une amine nitrée acyclique, cyclanique ou hétérocyclique

Abrégé

The invention relates to a combined steering and drag-reduction device intended for a missile comprising a base (13) and an upper part which are arranged in succession along a main axis (11) along which the missile is steered. Advantageously, the device comprises a pressurized-gas generator (35) and at least one lateral thruster (20) comprising: - at least one nozzle (38a, 38b), configured to deliver thrust, by expansion of the gas transmitted by the generator (35), which nozzle can be orientated about an axis substantially perpendicular to the main axis (11), - at least one stabilizing chamber (39), configured to expand the gas transmitted by the generator (35) and expel it through an exit section (43) of the base (13) substantially perpendicular to the main axis (11).

Classes IPC  ?

• F42B 10/40 - Dispositions pour augmenter la portée par la combustion d'une charge à vitesse de combustion lente, p. ex. projectiles du type à écoulement par le culot
• F42B 10/66 - Pilotage par variation de l'intensité ou de la direction de la poussée

Abrégé

The present application describes a brazing method for assembling a first part (10) and a second part (20) made from silicon carbide material, the first and second parts (10, 20) each comprising an assembly portion (11; 21) intended to be brazed with the assembly portion (21; 11) of the other part. The method comprises clamping together the assembly portions (11, 21) of the first and second parts (10, 20), interposing a brazing composition (41) between the assembly portions or close to said assembly portions, and brazing the assembly portions. The method further comprises a step of forming a plurality of ports (110, 210) in the assembly portions (11, 21) of the first and second parts. The ports are formed at predefined positions so as to align the ports (110) of the assembly portion (11) of the first part (10) with the ports (210) of the assembly portion (21) of the second parts (20) during the clamping step. An element (31) of a clamping member (30) is inserted through each pair of opposing ports (110, 210), each clamping member (30) applying a clamping force between the assembly portions (11, 21).

Classes IPC  ?

• B23K 1/00 - Brasage ou débrasage
• B23K 1/19 - Brasage ou débrasage tenant compte des propriétés des matériaux à braser
• B23K 1/20 - Traitement préalable des pièces ou des surfaces destinées à être brasées, p. ex. en vue d'un revêtement galvanique

Abrégé

A method for locally treating a portion (130) of a part (100) made from composite material comprising a fibrous reinforcement densified by a matrix, said material having internal porosity. The method comprises the following steps: - defining a quantity of infiltration composition (10) on the basis of the volume of the portion (130) of the part to be treated (100), the infiltration composition (10) comprising at least silicon, - placing the defined quantity of infiltration composition (10) in contact with the portion (130) of the part to be treated, - heat treating at a temperature greater than or equal to the melting temperature of the infiltration composition in such a way as to impregnate said portion with the treatment composition.

Classes IPC  ?

• C04B 41/85 - Revêtement ou imprégnation avec des substances inorganiques
• C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
• C04B 41/00 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle
• C04B 41/50 - Revêtement ou imprégnation avec des substances inorganiques
• C04B 41/52 - Revêtement ou imprégnation multiple
• F01D 5/00 - AubesOrganes de support des aubesDispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support

Abrégé

A method for producing an aerodynamic part comprising: - producing a preform (300) from a composite material made of a fibrous structure densified by a matrix, said preform having dimensions smaller than those of the aerodynamic part to be produced, - placing the preform made from composite material into a mould (400) having the same internal dimensions and shape as those of the aerodynamic part to be produced, - interposing a ceramic powder (50) between the preform made from composite material and the internal surface (402a) of the mould, said ceramic powder having a thermal expansion coefficient varying, at most, by 4.10"6.K_1 relative to the thermal expansion coefficient of the composite material of the preform, said ceramic powder further having a particle size of between 0.25 µm and 25 µm, - stabilising said powder in such a way as to form, around the preform made from composite material, a ceramic shell having the dimensions and the shape of the aerodynamic part to be produced.

Classes IPC  ?

• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• C04B 41/87 - Céramiques
• C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
• C04B 41/00 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle
• C04B 41/52 - Revêtement ou imprégnation multiple
• B28B 19/00 - Machines ou méthodes pour appliquer le matériau sur des surfaces pour former une couche permanente sur ces dernières
• C04B 41/45 - Revêtement ou imprégnation

Abrégé

The invention relates to a vane (10) for a turbine engine, made of a composite material including a fiber reinforcement obtained by means of three-dimensional weaving of threads and densified by a matrix. The vane includes a blade (12) and a vane base (14) that form a single part, the vane base having two substantially planar, opposite side flanks closed between two separate composite material plates (24) that are attached onto the side flanks of the vane base such as to form a bulb-shaped vane base.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

The part made of a matrix composite at least mainly made of ceramic is manufactured by a method comprising: producing a fibrous preform from silicon carbide fibres containing less than 1 at% oxygen; depositing on the fibres of the preform a boron nitride interphase, the deposit being carried out by gaseous phase chemical infiltration with a deposition rate lower than 0.3 um/h; carrying out a heat treatment for stabilising the boron nitride of the interphase, after deposition of the interphase, without prior exposure of the latter to an oxidising atmosphere before depositing a matrix layer on the interphase, the heat treatment being carried out at a temperature above 1300°C and at least equal to the maximum temperature subsequently encountered until densification of the preform by the matrix is complete; and next, densification of the preform by a matrix at least mainly made of ceramic.

Classes IPC  ?

• C04B 35/628 - Revêtement des poudres
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues

Abrégé

The invention relates to a method for manufacturing a casing (10), made of a composite material, for a gas-turbine engine, the method including the production of an outer hoop (100) including a flange (104) and a flat (106), the production of an inner hoop (200) having a smaller diameter than the outer hoop and including a flange (202) and a flat, the production of a plurality of casing arms (300) each including a blade (302) ending in a flange at each radial end, the arrangement in the respective flange of the hoops of a plurality of openings each intended for receiving a flange of a casing arm, and the assembly of the arms of the casing on the outer hoop and on the inner hoop by inserting the flanges of the casing arms in the openings in the hoops. The invention also relates to a casing made of a composite material obtained by such a method.

Classes IPC  ?

• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Classes IPC  ?

• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• B29C 70/22 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
• C04B 35/571 - Céramiques fines obtenues à partir de précurseurs polymères
• C04B 35/628 - Revêtement des poudres
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 37/00 - Liaison des articles céramiques cuits avec d'autres articles céramiques cuits ou d'autres articles, par chauffage
• B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices

Abrégé

The invention relates to a method for the braze-assembly of two parts (10, 20) made from a composite material, each part comprising an assembly face (10a, 20a) intended to be brazed to the assembly face of the other part. The method comprises the following steps: producing a plurality of cavities (101) in the assembly face (10a) of at least one of the two parts (10) made from composite material, at least one portion of said cavities opening onto one or more portions (10b, 10c) of the part that do not form part of the assembly face; inserting capillary elements (30) between the assembly faces of the parts made from composite material; placing a brazing composition (41) in contact with one portion of the capillary elements (30); liquefying the brazing composition (41) by means of heat treatment, such as to produce the capillary distribution of the molten brazing composition between the assembly faces (10a) of the parts of composite material.

Classes IPC  ?

• C04B 37/00 - Liaison des articles céramiques cuits avec d'autres articles céramiques cuits ou d'autres articles, par chauffage

Abrégé

The invention relates to a method for the braze-assembly of a first part (10) and a second part (20) made from a composite material, said first and second parts (10, 20) each comprising an assembly face (10a, 20a) intended to be brazed to the assembly face of the other part. The method comprises the following steps: producing at least one perforation (101) in the assembly face of the first part (10); inserting capillary elements (30) between the assembly faces (10a, 20a) of the first and second parts (10, 20) made from composite material; positioning the first and second parts (10, 20) facing one another, with the insertion of a slug (5) in each perforation in the first part (10); placing a brazing composition (41) in contact with part of the capillary elements (30); liquefying the brazing composition (41) by means of heat treatment, such as to produce the capillary distribution of the molten brazing composition between the assembly faces of the first and second parts of composite material.

Classes IPC  ?

• C04B 37/00 - Liaison des articles céramiques cuits avec d'autres articles céramiques cuits ou d'autres articles, par chauffage

Abrégé

Chemical vapour infiltration apparatus (600) for infiltrating three-dimensional porous preforms (20) mainly extending in a longitudinal direction, the apparatus comprising: a parallelepipedal reaction chamber (610), the side walls (612, 613) of the reaction chamber comprising heating means (615); and a plurality of stacks (50) of loading devices (10) placed in the reaction chamber (610), each loading device (10) being formed from a parallelepipedal recipient equipped with supporting elements intended to receive the porous preforms (20) to be infiltrated.

Classes IPC  ?

• C23C 16/458 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour supporter les substrats dans la chambre de réaction
• C23C 16/46 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour le chauffage du substrat
• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
• C23C 16/26 - Dépôt uniquement de carbone

Abrégé

The present invention relates to a method for supplying a missile engine with a storable propellant, which includes the consecutive steps of: 1) generating combustion gas by combustion of a pyrotechnic charge, and pressurising said storable propellant by means of said combustion gas; and then 2) selectively supplying said pressurised storable propellant to said engine. In a characteristic manner, said method is implemented with a pyrotechnic charge which generates combustion gases essentially made up of hydrogen.

Classes IPC  ?

• C01B 3/06 - Production d'hydrogène ou de mélanges gazeux contenant de l'hydrogène par réaction de composés inorganiques comportant un hydrogène lié électropositivement, p. ex. de l'eau, des acides, des bases, de l'ammoniac, avec des agents réducteurs inorganiques
• C06B 47/10 - Compositions dans lesquelles les composants sont conservés séparément jusqu'au moment de l'explosion ou de la combustion, p. ex. explosifs du type "Sprengel"Suspensions d'un composant solide dans une phase liquide normalement non explosive, y compris une phase aqueuse épaissie les composants comportant un propergol binaire un composant contenant du bore libre, un borane organique ou un composé binaire du bore, excepté avec l'oxygène
• F02K 9/50 - Alimentation en propergols utilisant du fluide pressurisé pour mettre les propergols sous pression

Abrégé

The invention relates to an actuated-stroke actuator having at least one additional pyrotechnic charge in order to adapt the anti-return resistance according to a desired development. According to the invention, at least one additional pyrotechnic charge (21a-21c) is placed in a recess communicating with the expansion chamber (24) of the actuator (11).

Classes IPC  ?

• F15B 15/19 - Vérins pyrotechniques
• B60R 21/38 - Protection des personnes extérieures au véhicule, p. ex. des piétons utilisant des moyens pour soulever les capots

Abrégé

Charging device (100) for densifying porous preforms (160-163) of stackable shape in a reaction chamber of an infiltration furnace by controlled flow chemical vapour infiltration, the device comprising: - a support plate (110), - a first stack of a plurality of lower rings (140-144) placed on the support plate (110) and comprising a plurality of injection orifices extending between the outer periphery and the inner periphery of each ring, - a second stack of a plurality of upper rings (150-154) comprising a plurality of discharge orifices extending between the outer periphery and the inner periphery of each ring, - a first non-porous wall (130) of a shape and size identical to those of the porous preforms (160-163) that are to be densified and arranged on the support plate (110) inside the lower rings (140-144) of the first stack, said first non-porous wall extending between the support plate and the upper ring situated at the base of the second stack, - a second non-porous wall (170) of a shape and size identical to those of the porous preforms (160-163) that are to be densified, said second non-porous wall extending between the lower ring (143) situated at the top of the first stack and the upper ring (154) situated at the top of the second stack.

Classes IPC  ?

• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
• C23C 16/458 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour supporter les substrats dans la chambre de réaction
• C23C 16/46 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour le chauffage du substrat
• C04B 35/00 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques

Abrégé

A normally closed electrical switch having a sliding assembly actuated on opening, for example by a pyrotechnic gas generator. Prior to actuation, a conductive portion of the sliding assembly (21) is in tight contact with two axially offset coaxial rings (13a, 14a) belonging respectively to two electrically conductive pads (13, 14), and after the actuator is triggered, the upstream pad (13) is released from the conductive portion of the sliding assembly. According to the invention, the sliding assembly comprises a tube provided with a slot extending along the entire length of same, and the conductive portion of the sliding assembly consists of all or a portion of said slotted tube, the clamping force between the conductive portion and the primary electrically conductive pads being provided by the elasticity of the slotted tube.

Classes IPC  ?

• H01H 39/00 - Dispositifs de commutation actionnés par une explosion produite à l'intérieur du dispositif et amorcée par un courant électrique

Abrégé

A device for atomising (100) a liquid (L), comprises a container (10) containing the liquid to be atomised (L), at least one liquid ejection member (20), in communication with said container (10), and a pyrotechnic gas generator (30) for pressurising the liquid inside said container and propelling said pressurised liquid out of said container. According to the invention, the ejection member (20) is, at least in one operating mode, in communication with the gas generator (30) in such a way as to be able to be supplied with the gas generated by said generator (30).

Classes IPC  ?

• A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice
• A62C 13/70 - Extincteurs portatifs sous pression permanente ou mis sous pression immédiatement avant l'emploi la substance extinctrice et le gaz comprimé étant emmagasinés dans des récipients distincts caractérisés par les moyens pour décharger le gaz comprimé
• B05B 7/00 - Appareillages de pulvérisation pour débiter des liquides ou d'autres matériaux fluides provenant de plusieurs sources, p. ex. un liquide et de l'air, une poudre et un gaz
• B05B 7/04 - Pistolets pulvérisateursAppareillages pour l'évacuation avec des dispositifs permettant le mélange de liquides ou d'autres matériaux fluides avant l'évacuation
• B05B 7/06 - Pistolets pulvérisateursAppareillages pour l'évacuation avec un orifice de sortie en entourant un autre situé approximativement dans le même plan
• A62C 31/07 - Buses spécialement conçues pour la lutte contre l'incendie avec au moins deux sorties pour des substances différentes

Abrégé

A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

Method for producing a component made of composite comprising a fibrous reinforcement that is densified with a matrix, said method involving the following steps: - creation of a fibrous texture (10) by weaving filaments, said fibrous texture having a determined initial mean fibre content, - densification of the fibrous texture using a matrix. According to the invention, the fibrous texture (10) is, prior to densification, subjected to one or more jets (120) of water under pressure so as to reduce the mean fibre content in the texture to a value of between 20% and 45%.

Classes IPC  ?

• D06C 29/00 - Finissage ou apprêtage de tissus textiles non prévus dans les autres groupes de la présente sous-classe
• B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
• C04B 35/628 - Revêtement des poudres
• B32B 18/00 - Produits stratifiés composés essentiellement de céramiques, p. ex. de produits réfractaires

Abrégé

The invention relates to a method for the treatment of silicon carbide fibres, comprising a step involving the chemical treatment of fibres with an aqueous acid solution containing hydrofluoric acid and nitric acid but free of acetic acid in order to remove the silica present on the surface of fibres and to form a layer of microporous carbon. The invention also relates to a method for the production of a fibrous preform, comprising the formation of a fibrous structure comprising treated silicon carbide fibres and the use of said preform for the production of a part made from composite material.

Classes IPC  ?

• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 41/91 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle de céramiques uniquement impliquant l'enlèvement d'une partie des matières des objets traités, p. ex. par attaque chimique
• C23C 16/02 - Pré-traitement du matériau à revêtir
• C04B 35/622 - Procédés de mise en formeTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques

Abrégé

The invention relates to a device (200) providing protection against lightning and intended to be placed on a structure (100) that is to be protected, and comprising: a surface coating comprising at least one coat of conducting paint (202), a plurality of electrically conducting elements (204) positioned in a spaced-apart manner on the structure, said elements being in contact with the coat of conducting paint (202), a protective coating (205) applied to the surface coating and comprising a thermally insulating and electrically conducting material, the protective coating (205) partially covering the electrically conducting elements (204).

Classes IPC  ?

• B64D 45/02 - Dispositifs de protection contre la foudreDéperditeurs de potentiel
• B64G 1/58 - Protection thermique, p. ex. boucliers thermiques
• F42B 15/34 - Protection contre la surchauffe ou l'irradiation, p. ex. boucliers thermiquesDispositions particulières pour le refroidissement

Abrégé

The invention concerns an afterbody assembly (400) of an aircraft engine comprising an exhaust housing (100) made from a metal material comprising a plurality of arms (130) extending radially between an inner shell (110) and an outer shell (120). The assembly comprises at least one axisymmetric part (200) made from a composite material extending between an upstream end (201) secured to said exhaust housing (100) and a free downstream end (202). According to the invention, the axisymmetric part (200) comprises, at the upstream end (201) of same, an annular portion (210) comprising a plurality of slots (211) together delimiting a plurality of elastic fastening tabs (212). Each slot engages with an arm (130) of the exhaust housing which further comprises attachment portions (131) to which the elastic fastening tabs (212) are secured.

Classes IPC  ?

• F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
• F02K 1/04 - Montage d'un cône d'échappement dans la tubulure de jet

Abrégé

The invention concerns a holding tool (100) for at least one part (150) made from metal material intended to be heat treated or hot shaped, said tool comprising: - a fixed support structure (110) having a determined shape corresponding to the general shape of each part made from metal material to be held, - first holding elements (1161-1261) disposed to one side of each part, - second holding elements (1162-1262) disposed to the other side of each part, - at least one elastic spring element (130-134) placed between the support structure (110) and each first or second holding element (1161-1261; 1162-1262) so as to hold the part for the entire duration of a heat treatment. The support structure (110), the first and second holding elements (1161-1261, 1162-1262) and the elastic element or elements (130-134) are made from a thermostructural composite material.

Classes IPC  ?

• C21D 1/673 - Dispositifs pour trempe pour la trempe en coquille
• C21D 9/00 - Traitement thermique, p. ex. recuit, durcissement, trempe ou revenu, adapté à des objets particuliersFours à cet effet
• B21D 1/14 - Redressage des bâtis ou châssis
• F27D 5/00 - Supports, grilles ou appareillage analogue pour la charge à l'intérieur du four
• C22F 1/18 - Métaux réfractaires ou à point de fusion élevé ou leurs alliages

Abrégé

A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.

Classes IPC  ?

• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F04D 29/38 - Ailettes
• G06F 17/50 - Conception assistée par ordinateur

Abrégé

The invention relates to a gas turbine aero engine afterbody assembly comprising a casing (40), an annular jet pipe (38) positioned in the downstream continuation of the casing, and a plurality of tubes (42) positioned around the jet pipe and intended to inject a fluid into the downstream end of the jet pipe, the jet pipe being fixed to the casing via the tubes.

Classes IPC  ?

• F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
• F02K 1/38 - Introduction d'air à l'intérieur du jet

Abrégé

The invention relates to an aeronautical engine exhaust cone (1) extending from upstream to downstream along a longitudinal axis. The cone (1) comprises a structural core (10) made of composite material formed of an axisymmetric component (11) which at its upstream end has an upstream flange (12) and at its downstream end has a downstream flange (13), the core providing the cone with its structural strength. The cone further comprises an acoustic attenuation system (20) made of a composite material and attached to the structural core (10).

Classes IPC  ?

• F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
• F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
• F02C 7/24 - Isolation thermique ou acoustique

Abrégé

The invention relates to a spacecraft (1), in particular a satellite or probe, which can be used to carry out high-thrust or high specific impulse movements. According to the invention, the spacecraft (1) includes at least one solid propellant motor (10-14) and at least one electric thruster (20-24).

Classes IPC  ?

• B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
• B64G 1/42 - Aménagements ou adaptations des systèmes fournissant l'énergie

Abrégé

The invention relates to a part made of a ceramic matrix composite comprising a fibrous reinforcement made of carbon or ceramic fibres, and a mainly ceramic sequenced matrix comprising first matrix layers made of a crack deviator alternating with second matrix layers made of a ceramic. An interphase coating is interposed between the fibres and the matrix, the interphase coating adhering to the fibres and to the matrix and being formed from at least one sequence consisting of a first elementary layer made of carbon, which is optionally doped with boron, surmounted with a second elementary layer made of a ceramic, the external elementary layer of the interphase coating being a ceramic layer the external surface of which is formed by ceramic grains the size of which essentially lies between 20 nanometres and 200 nanometres, with the presence of grains larger than 50 nanometres in size providing the external surface with a roughness ensuring mechanical bonding with the adjacent matrix phase.

Classes IPC  ?

• C04B 35/563 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de bore
• C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 35/628 - Revêtement des poudres

Abrégé

The invention relates to a method for treating silicon carbide fibres (20), comprising a reactive gaseous phosphation heat treatment such as to form, around each fibre (20), an oxidation-protective coating (200) including a surface layer of silicon pyrophosphate crystals (201) and at least one subjacent bilayer system (210) comprising a layer of a phosphosilicate glass (211) and a layer of microporous carbon (212).

Classes IPC  ?

• C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
• C04B 35/628 - Revêtement des poudres

Abrégé

The invention relates to the manufacture of a composite material part, includes the steps of: creating a consolidated fibrous preform, the fibers of the preform being carbon or ceramic fibers and being coated with an interphase formed of at least one pyrolytic carbon (PyC) or boron-doped carbon (BC) layer; obtaining a partially densified, consolidated fibrous preform, the partial densification including the formation, on the interphase, of a first matrix phase including a plurality of layers of self-healing material alternating with one or more PyC or BC layers; and pursuing densification by scattering carbon and/or ceramic powder within the partially densified, consolidated preform and permeating with fused silicon or a liquid composition predominantly formed of silicon.

Classes IPC  ?

• C04B 35/573 - Céramiques fines obtenues par frittage par réaction
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 35/628 - Revêtement des poudres
• C04B 41/45 - Revêtement ou imprégnation
• C04B 41/50 - Revêtement ou imprégnation avec des substances inorganiques
• C04B 41/52 - Revêtement ou imprégnation multiple
• C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes

Abrégé

A turbomachine vane (10) made from composite material comprises a hollow blade (12) including an internal passage (11) extending along the entire length thereof, an internal platform (14) and an external platform (16). The blade is extended on the external side of the external platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing, said attachment portions being formed by attachment lugs (24, 26, 28) extending from external longitudinal ends of lower surface (12a) and upper surface (12b) walls of the blade, with the fibrous reinforcement texture of the composite material extending continuously between said walls and the attachment lugs.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

According to the invention, a fibrous blank is formed by means of multilayer weaving, said blank having a longitudinal direction corresponding to that of the vane to be produced and the thickness thereof comprising a first portion (102) with multiple interwoven layers of yarns, a second woven portion and a third woven portion. The first portion is located between the second portion and the third portion and it is interwoven therewith along only part of the longitudinal dimension thereof. A preform of the vane to be produced is formed by unfolding, on both sides of the first portion, segments (104a, 106a, 104b, 106b) of the second and third portions that are not connected to the first portion, by shaping the first portion in order to form a preform part for the blade of the vane to be produced, and by shaping the unfolded segments of the second and third portions in order to form preform parts for the internal and external platforms of the vane to be produced, and the vane preform is densified using a matrix in order to obtain a vane made from composite material and including integrated platforms.

Classes IPC  ?

• B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
• B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
• B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
• B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

The invention relates to a attachment device (240) for attaching a hollow part consisting of two opposing walls to at least one structural part. The device includes a one-piece body (241) made of a metal material and having two main surfaces (242, 243) extending longitudinally between first and second ends (244, 245) of said body. Each main surface (242; 243) includes a bearing portion (2420; 2430) in the vicinity of the first end (244) of said body, which bearing portion is intended to be pressed against an inner surface of one of the two walls of the hollow part, each bearing portion (2420; 2430) comprising an attachment opening (2421) for receiving an attachment member. The bearing portions (2420; 2430) are separated from one another by a slot (246) extending from the first end (244) of said body (241) to a predetermined depth in said body.

Classes IPC  ?

• F02K 1/04 - Montage d'un cône d'échappement dans la tubulure de jet
• F02K 1/80 - Accouplements ou assemblages
• F02D 9/04 - Commande des moteurs par étranglement des conduits d'amenée de l'air ou du mélange air-combustible ou par étranglement des conduits d'échappement par étranglement des conduits d'échappement
• F23R 3/18 - Moyens de stabilisation de la flamme, p. ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction
• F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines

Abrégé

Single blade vanes each having an inner platform (114), an outer platform (116) and a blade (118) are obtained by three-dimensional weaving of a fibrous blank formed as a single piece, by shaping the fibrous blank to obtain a one-piece fibrous preform, by densifying the preform with a matrix to obtain a composite vane forming a single piece with built-in inner and outer platforms. Several vanes are assembled and joined together to form a composite multi-blade turbine nozzle guide vanes sector or compressor guide vanes sector, connection being achieved through a process involving at least one step chosen from: a step of connection using brazing and a step of connection using codensification with a matrix of vanes that are assembled at an intermediate stage in their densification. The inner or outer platform of a first vane comprises an inner or outer platform part that makes up part of the shroud and is connected to an inner or outer platform part of an adjacent second vane in a connecting zone extending over at least part of the interior surface of the inner platform part that makes up part of the shroud of the first vane and/or over at least part of the outer surface of the outer platform part that makes up the shroud of the first vane.

Classes IPC  ?

• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
• B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle

Abrégé

The invention relates to a gas generator (10) including a body (12) defining at least one portion of a combustion chamber (20), said portion housing a primary pyrotechnic charge (16) suitable for generating gases in the combustion chamber (20) when said charge is ignited, and a slide valve (60) situated outside of said body (12) and defining therewith a second chamber (66) housing a secondary pyrotechnic charge (74), the self-ignition temperature of which is lower than that of the primary pyrotechnic charge (16). A channel (50) is formed inside the body (12) to enable the gases to flow out of the combustion chamber (20). According to the invention, the slide valve (60) seals off said channel when said slide valve is in a first position and, as a result of the gases released by said secondary pyrotechnic charge (74), the slide valve is suitable for shifting into a second position in which the channel (50) is no longer sealed off, thereby enabling the gases contained in the combustion chamber (20) to flow outwards.

Classes IPC  ?

• F42B 3/00 - Cartouches de sautage, c.-à-d. enveloppes avec explosif
• F42B 3/04 - Cartouches de sautage, c.-à-d. enveloppes avec explosif pour la production de gaz sous pression
• F42B 39/20 - Emballages ou munitions munis de soupapes pour équilibrer la pressionEmballages ou munitions munis de bouchons pour réduire la pression, p. ex. de bouchons fusibles

Abrégé

A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• C04B 35/571 - Céramiques fines obtenues à partir de précurseurs polymères
• C04B 35/628 - Revêtement des poudres
• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• D03D 11/02 - Tissus comportant des poches, tubes, boucles, plis, plissés ou rabats
• D03D 25/00 - Tissus non prévus ailleurs
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• B23P 15/04 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe d'aubes de turbine ou d'organes équivalents, en plusieurs pièces
• B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement

Abrégé

Loading device (10) for densification via chemical infiltration in steam phase in directed flow, in a reaction chamber of an infiltration oven, of three-dimensional porous substrates (20) extending primarily in a longitudinal direction, said device comprising an annular loading level (11) formed by first and second annular vertical units (110, 111) distributed concentrically in relation to one another and delimiting between one another an annular loading area (13) for the porous substrates to be densified. First and second plates (112, 113) respectively cover the lower element and the upper element of the annular loading area (13). The first and second annular vertical units (110, 111) each comprise supporting members (1100, 1110) distributed in the annular loading area (13) in such a manner as to define between them unit loading cells (14), each unit loading cell being intended for receiving a substrate to be densified. The device additionally comprises gas supply orifices (1102) and gas evacuation orifices (1112) in the vicinity of each unit loading cell (14).

Classes IPC  ?

• C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques

Abrégé

The main subject of the present invention is a process for processing a paste (5) containing a solid filler (C) with a view to extracting at least one part of said solid filler (C). Said method comprises continuously: mixing, in a mixer (8), said paste (5) with a liquid solvent (3), a solvent for said at least one part of said solid filler (C), with a view to dissolving, at least partially, said at least one part of said solid filler (C) in said solvent; recovering, after said mixing, a biphasic system (15) comprising, on the one hand, a solution (30) enclosing at least one fraction of said at least one part of said solid filler (C), dissolved in said solvent (3), and on the other hand, a solid residue (50) of said paste (5); and then, separating said solution (30) and said solid residue (50) from said paste (5).

Classes IPC  ?

• B01D 11/02 - Extraction par solvants de solides
• C06B 21/00 - Appareils ou méthodes pour la mise en œuvre des explosifs, p. ex. mise en forme, coupage, séchage
• B01F 5/06 - Mélangeurs dans lesquels les composants du mélange sont pressés ensemble au travers de fentes, d'orifices, ou de tamis

Abrégé

The invention relates to a turbine nozzle or compressor stator vane that includes sectors (12) made of a CMC material, each of which has an inner platform (14), an outer platform (16), and blades (18). A support ring (50) made of an abradable material consists of sectors, each of which has upstream (55a) and downstream (55b) attachment lugs. Each of the inner platforms (14) has, on the inner side thereof, an upstream hook (15a) and a downstream hook (15b), and the support ring made of abradable material is supported by the nozzle or by the stator vane by mutual engagement, without rigid connection, of end portions of the upstream attachment lugs and upstream hooks, and of end portions of the downstream attachment lugs and downstream hooks.

Classes IPC  ?

• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

The invention relates to a method, including: depositing, onto the entire surface of a substrate, a refractory-cement paste mainly consisting of silica and alumina and mixed with a liquid, the cement paste filling in the hollow portions of the raised pattern of the surface; performing a heat treatment in order to harden the cement after the latter has set and obtain a first layer (22) of refractory-cement coating; depositing, onto the first layer, a slurry consisting of a glass frit suspended in a liquid and mainly consisting of a powder consisting of silica, boron oxide, alumina and at least one alkaline metal oxide; and performing a heat treatment for coating by softening and spreading the glass in order to obtain a second coating layer (24) forming a glaze covering the first layer, the composition of the glass frit being selected so as to form glass having a coating temperature of less than 1100°C and a glass-transition temperature of less than 750°C.

Classes IPC  ?

• C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

The invention relates to single-blade vanes, each of which has an inner platform (114), an outer platform (116), and a blade (118), and which are obtained by means of the three-dimensional weaving of an integral fibrous blank, shaping the fibrous blank so as to obtain an integral fibrous preform, and densifying the preform with a matrix so as to obtain a vane made of a composite material forming an integral part with inner and outer platforms. A plurality of vanes are assembled and linked together so as to form a multi-blade sector of a turbine nozzle or compressor stator vane made of a composite material.

Classes IPC  ?

• B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices

Abrégé

A refractory material that is high-temperature resistant in an oxidizing medium contains at least hafnium boride and tantalum boride, the hafnium and the tantalum being present in the refractory material exclusively in compound form.

Classes IPC  ?

• C04B 35/515 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes
• C04B 35/58 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de borures, nitrures ou siliciures
• C04B 41/52 - Revêtement ou imprégnation multiple
• C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
• C04B 35/56 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures
• C04B 41/00 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle

Abrégé

A vibration damper between outer platforms of adjacent composite-material blades of a rotor wheel of a turbine engine, the damper including a strip for inserting lengthwise in tangential cavities that are formed facing each other in the outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel.

Classes IPC  ?

• F01D 5/10 - Dispositifs antivibratoires
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 5/22 - Connections aube à aube, p. ex. par emboîtement

Abrégé

The invention relates to a turbine nozzle guide vane assembly comprising a plurality of vanes (12) made of composite material, each vane comprising an inner platform (14), an outer platform (16) having, on the outer side, attachment tabs (162, 164) and at least one blade section (18) extending between the inner and outer platforms and secured thereto. The vane attachment tabs are engaged on a metal mounting ring (20) supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes and forming a separate mounting piece between the vanes and a turbine casing (40).

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.

Classes IPC  ?

• F01D 5/22 - Connections aube à aube, p. ex. par emboîtement
• F01D 5/26 - Dispositifs antivibratoires non limités à la forme ou à la structure des pales ou aux connections aube à aube

Abrégé

A layout of a blisk includes two inserts housed between the bulb of the blade and the wall of a groove in a disk to compensate for variations in inclination between the overhanging faces of the groove and the upper faces of the bulb at their central part. This construction makes it possible to select blades for which upper faces of the bulb are slightly inclined relative to the radial direction, which facilitates their construction from a composite material.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

The invention relates to a turbine rotor including a plurality of blades (100) made of a composite material including a fibrous reinforcement compregnated by a mould, each blade (100) including a blade body (120) that extends between an inner end (101) including a blade root (110) and an outer end (102) forming the tip (140) of the blade (100). The rotor also includes blade root elements (200) made of a composite material including a fibrous reinforcement compregnated by a mould, each blade root element including an opening (201) into which the outer end (102) of a blade (100) is inserted. The portion (126a) of the outer end (102) of each blade (100) extending above the blade root element (200) comprises a hole or recess (127) into which a locking element (230) is placed.

Classes IPC  ?

• F01D 5/22 - Connections aube à aube, p. ex. par emboîtement
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• B29C 70/22 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
• B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
• B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe

Abrégé

The invention relates to an in-flight attitude control and direct thrust flight control system which includes a propulsion body (20) and a plurality of valves capable of generating sidewise thrust when placed in communication with the propulsion body. The valves are distributed into two sets of valves (24, 26) spaced apart from one another towards the front and towards the rear of the propulsion body, in a substantially symmetrical manner relative to the centre of gravity of the vehicle, located on a longitudinal axis (A) thereof. Each set includes a first pair of valves generating thrust in opposite directions, along axes that are not aligned and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions, along axes that are not aligned and are parallel to a second axis, the first and second axes being separate and perpendicular to the longitudinal axis of the vehicle.

Classes IPC  ?

• F42B 10/66 - Pilotage par variation de l'intensité ou de la direction de la poussée
• B64G 1/26 - Appareils de guidage ou de commande, p. ex. de commande d'assiette par jets